# US 8,740,149 B1 · Flow channels > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,740,149 B1 - Document ID: US8740149B1 - Status: Granted - Kind: B1 - Application number: 13/908,522 - Filed: 2013-06-03 - Granted: 2014-06-03 - Earliest claimed: 2010-12-13 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Gregory G. Thumann - Web page: https://patentgrep.com/patent/US8740149B1 ## CPC - B64C 7/00: Structures or fairings not otherwise provided for - B64C 21/00: Influencing air flow over aircraft surfaces by affecting boundary layer flow - B64C 23/06: by generating vortices - B64D 39/00: Refuelling during flight - B64C 2230/26: by using rib lets or hydrophobic surfaces - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The present disclosure relates to flow channels comprising a channel length having a first portion approximately parallel to the maximum waterline thickness location of a body and at least a second portion non-parallel thereto, a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of the surface of the body, and at least a portion of the free edge being arcuate. A method comprises providing the fluid channel attachable to a body, modifying resultant vortices and reducing or minimizing shock formations or separation regions of the freestream. ## Claims ### Claim 1 A flow channel attachable to a body positioned on a wing of an aerospace vehicle, the flow channel comprising: a channel length having a first portion essentially parallel to a maximum waterline thickness location of the body and at least a second portion non-parallel to the maximum waterline thickness location of the body; a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a continuous free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of a surface of the body. ### Claim 2 (depends on 1) The flow channel of claim 1, wherein the leading edge is rounded in planform and has a profile essentially perpendicular to the surface of the body to eliminate or reduce premature vortex shedding. ### Claim 3 (depends on 1) The flow channel of claim 1, wherein the trailing edge has an angular termination planform configured to shed vortical air structures. ### Claim 4 (depends on 1) The flow channel of claim 1, wherein the free edge varies from linearity for about the first two thirds of the channel length from the leading edge and wherein the free edge arcuately changes in approximately the last third of the channel length from the leading edge. ### Claim 5 (depends on 1) The flow channel of claim 1, wherein the predetermined height increases from the leading edge to the trailing edge. ### Claim 6 (depends on 1) The flow channel of claim 1, wherein the channel is configured for positioning on one or both of the inboard side surface of the body and the outboard side surface of the body. ### Claim 7 (depends on 1) The flow channel of claim 1, wherein a portion of the free edge has a pitch angle relative to a surface tangent of the body at the attachment edge of the flow channel between about 45 degrees to about 135 degrees. ### Claim 8 (depends on 7) The flow channel of claim 7, wherein the pitch angle is variable along one or more portions of the length of the flow channel. ### Claim 9 (depends on 7) The flow channel of claim 7, wherein the pitch angle is predetermined along one or more portions of the length of the flow channel to maximize vortex shedding of a free stream traveling at a velocity of between about 0.2 to 0.9 mach. ### Claim 10 (depends on 1) The flow channel of claim 1, wherein at least a portion of the free edge is tapered. ### Claim 11 A method of reducing vibration and/or buffet of an aerospace vehicle having a body on a wing, the method comprising providing at least one flow channel attachable to the body, the flow channel comprising a channel length having a first portion parallel to a maximum waterline thickness location of the body and at least a second portion non-parallel to the maximum waterline thickness location of the body; a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a continuous free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of a surface of the body; modifying resultant vortices formed at air speeds between about 0.2 to about 0.9 mach; and reducing or minimizing shock formations or separation regions of the freestream in proximity to the body and/or body attachment and wing. ### Claim 12 (depends on 11) The method of claim 11, wherein reducing or minimizing shock formations comprises driving regions of complex shock formations and/or pockets of separation aft of the wing and/or the body. ### Claim 13 (depends on 11) The method of claim 11, wherein the channel is positioned on one or both of the inboard side surface of the body and the outboard side surface of the body. ### Claim 14 (depends on 11) The method of claim 11, wherein the plurality of flow channels includes one or more flow channels attached on one or both of the inboard and the outboard sides of the body. ### Claim 15 (depends on 11) The method of claim 11, wherein the leading edge eliminates or limits shedding of the desired vortical air structures. ### Claim 16 (depends on 11) The method of claim 11, wherein the predetermined height of the flow channel further provides a target shedding vortex strength. ### Claim 17 (depends on 11) The method of claim 11, wherein the leading edge is configured for positioning between an angle of about zero to about five degrees downwardly relative to the body longitudinal axis. ### Claim 18 (depends on 11) The method of claim 11, wherein the free edge varies from linearity for about the first two thirds of the channel length from the leading edge and wherein the free edge arcuately changes in approximately the last third of the channel length from the leading edge. ### Claim 19 (depends on 11) The method of claim 11, wherein the predetermined height increases from the leading edge to the trailing edge. ### Claim 20 (depends on 11) The method of claim 11, wherein the body is a Wing Aerial Refueling Pod (WARP). ### Claim 21 An aerospace vehicle comprising: a wing; a body coupled to the wing; and a flow channel coupled to the body, the flow channel comprising: a channel length having a first portion essentially parallel to a maximum waterline thickness location of the body and at least a second portion non-parallel to the maximum waterline thickness location of the body; a leading edge at a first end of the channel length, the leading edge separated from a trailing edge by a continuous free edge along the channel length, the free edge projecting a predetermined height from an attaching edge attachable to at least a portion of a surface of the body. ### Claim 22 (depends on 21) The aerospace vehicle of claim 21, wherein the free edge varies from linearity for about the first two thirds of the channel length from the leading edge and wherein the free edge arcuately changes in approximately the last third of the channel length from the leading edge. ### Claim 23 (depends on 21) The aerospace vehicle of claim 21, wherein the aerospace vehicle is a tanker aircraft. ### Claim 24 (depends on 21) The aerospace vehicle of claim 21, wherein the body is a store. ### Claim 25 (depends on 24) The aerospace vehicle of claim 24, wherein the store is a Wing Aerial Refueling Pod (WARP).